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公开(公告)号：US20090241507A1
公开(公告)日：2009-10-01
申请号：US12060557
申请日：2008-04-01
CPC分类号： F02C5/00 , F02C7/08 , F02C7/143 , Y02T50/675
摘要： A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage.
摘要翻译： 基于地面的发电系统包含至少两个压缩机级，燃烧级和涡轮级。 中间冷却器位于两个压缩机级之间，并且再生器位于压缩机级和燃烧级之间。 燃烧阶段包括脉冲爆震燃烧器和恒定体积燃烧器中的至少一个。 燃烧阶段的下游是涡轮机阶段。 用于再生器的热量由涡轮级供给。 此外，还包括旁路流动装置，其将燃烧阶段上游的流动重新引导到燃烧阶段的下游以及涡轮级的上游。
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2.发明申请PULSE DETONATION COMBUSTOR VALVE FOR HIGH TEMPERATURE AND HIGH PRESSURE OPERATION 审中-公开用于高温和高压运行的脉冲爆炸式气动阀公开(公告)号：US20090139199A1
公开(公告)日：2009-06-04
申请号：US12271082
申请日：2008-11-14
申请人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser , James Fredric Wiedenhoefer , David Chapin , Kevin Hinckley , Pierre Francois Pinard
发明人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser , James Fredric Wiedenhoefer , David Chapin , Kevin Hinckley , Pierre Francois Pinard
IPC分类号： F02C5/12
摘要： A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor.
摘要翻译： 脉冲爆震燃烧器阀组件包含至少一个具有入口部分的脉冲爆燃燃烧器，空气和/或燃料通过该入口部分进入燃烧室的腔室。 环形旋转阀部分定位成与脉冲爆震燃烧器的外表面相邻并且与脉冲爆震燃烧器同心地定位，使得环形旋转阀部分可相对于燃烧器旋转。 环形旋转阀部分包含至少一个入口部分，空气和/或燃料通过该入口部分进入脉冲爆震燃烧器的入口部分。
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公开(公告)号：US20090133377A1
公开(公告)日：2009-05-28
申请号：US12270980
申请日：2008-11-14
申请人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser
发明人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser
IPC分类号： F02C5/02
摘要： An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is positioned such that the inlet portion of the pulse detonation combustor is located forward of an outlet of the compressor stage with respect to the engine. The pulse detonation combustor is angled with respect to a centerline of the engine.
摘要翻译： 发动机包含压缩机级，脉冲爆震燃烧级和涡轮级。 脉冲爆震燃烧阶段包含至少一个具有入口部分的脉冲爆震燃烧器。 脉冲爆震燃烧器被定位成使得脉冲爆震燃烧器的入口部分相对于发动机位于压缩机级的出口的前方。 脉冲爆震燃烧器相对于发动机的中心线成角度。
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公开(公告)号：US07721523B2
公开(公告)日：2010-05-25
申请号：US12060557
申请日：2008-04-01
IPC分类号： F02C7/10
CPC分类号： F02C5/00 , F02C7/08 , F02C7/143 , Y02T50/675
摘要： A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage.
摘要翻译： 基于地面的发电系统包含至少两个压缩机级，燃烧级和涡轮级。 中间冷却器位于两个压缩机级之间，并且再生器位于压缩机级和燃烧级之间。 燃烧阶段包括脉冲爆震燃烧器和恒定体积燃烧器中的至少一个。 燃烧阶段的下游是涡轮机阶段。 用于再生器的热量由涡轮级供给。 此外，还包括旁路流动装置，其将燃烧阶段上游的流动重新引导到燃烧阶段的下游以及涡轮级的上游。
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5.发明申请MULTI-TUBE, CAN-ANNULAR PULSE DETONATION COMBUSTOR BASED ENGINE WITH TANGENTIALLY AND LONGITUDINALLY ANGLED PULSE DETONATION COMBUSTORS 审中-公开多管，CAN-ANNULAR PULSE爆炸式燃烧器基于发动机，具有纵向和纵向喷射脉冲爆炸燃烧器公开(公告)号：US20090266047A1
公开(公告)日：2009-10-29
申请号：US12271070
申请日：2008-11-14
申请人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser
发明人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser
IPC分类号： F02C5/02
CPC分类号： F02C5/02 , F02C5/12 , F05D2250/322 , F23C15/00 , F23D14/42 , F23R3/425 , F23R7/00 , F23R2900/00014
摘要： An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine.
摘要翻译： 发动机包含压缩机级，脉冲爆震燃烧级和涡轮级。 脉冲爆震燃烧阶段包含至少一个具有入口部分的脉冲爆震燃烧器。 脉冲爆震燃烧器相对于发动机的中心线纵向和/或切向地定向。
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6.发明申请公开(公告)号：US20080155959A1
公开(公告)日：2008-07-03
申请号：US11963212
申请日：2007-12-21
申请人： Adam Rasheed , Anthony John Dean , James Fredric Wiedenhoefer , Venkat Eswarlu Tangirala , Narendra Digamber Joshi
发明人： Adam Rasheed , Anthony John Dean , James Fredric Wiedenhoefer , Venkat Eswarlu Tangirala , Narendra Digamber Joshi
CPC分类号： F02C5/00 , F01D9/023 , F05D2250/141 , F05D2260/16 , Y02T50/675
摘要： A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the exhaust flow. The transition piece provides a non-expanding path for the exhaust flow through the transition piece, and directs the flow so as to be effective in driving the turbine when it reaches the end of the transition piece.
摘要翻译： 在燃气涡轮发动机内使用的过渡件提供了来自一个或多个压力升高燃烧器的排气和用于从排气流中提取工作的下游涡轮之间的路径。 过渡件为通过过渡件的排气提供非扩张路径，并引导流动，以便在涡轮到达过渡件的端部时有效驱动涡轮机。
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7.发明申请MODULATION OF INLET MASS FLOW AND RESONANCE FOR A MULTI-TUBE PULSE DETONATION ENGINE SYSTEM USING PHASE SHIFTED OPERATION AND DETUNING 审中-公开使用相位转换操作和分离的多管脉冲爆震发动机系统的输入质量流量和谐振的调节公开(公告)号：US20100242436A1
公开(公告)日：2010-09-30
申请号：US12415677
申请日：2009-03-31
IPC分类号： F02K5/02
CPC分类号： F02C5/10
摘要： An engine contains a compressor stage, a plurality of pulse detonation combustors and a plurality of inlet valves, where the inlet valves direct a mass flow into the pulse detonation combustors. A control system controls at least one of a phase shift, firing frequency and a τopen/τcycle ratio of the pulse detonation combustors based on a mass flow and/or a resonance within the engine.
摘要翻译： 发动机包括压缩机级，多个脉冲爆震燃烧器和多个入口阀，其中入口阀将质量流引导到脉冲爆震燃烧器中。 控制系统基于发动机内的质量流和/或谐振来控制脉冲爆震燃烧器的相移，发射频率和τopen/τ循环比中的至少一个。
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8.发明授权Hot gas path component cooling for hybrid pulse detonation combustion systems 有权混合脉冲爆震燃烧系统的热气路径组件冷却公开(公告)号：US08978387B2
公开(公告)日：2015-03-17
申请号：US12974085
申请日：2010-12-21
申请人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
发明人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
CPC分类号： F02C5/02 , F02C7/18 , F02C9/18 , F05D2260/205 , F23C15/00
摘要： The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.
摘要翻译： 通过混合脉冲爆震燃烧系统的核心的流动通过压缩机，然后分离成直接通向燃烧器的主流，以及旁路流，其被路由到系统的一部分以用于 系统的酷组件。 旁路流被引导到脉冲爆震燃烧器的喷嘴。 然后将流体通过芯被提取的下游的核心传回初级流中。
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9.发明申请HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS 审中-公开用于混合脉冲爆震燃烧系统的热气路径组件冷却公开(公告)号：US20120151895A1
公开(公告)日：2012-06-21
申请号：US12974031
申请日：2010-12-21
申请人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
发明人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
CPC分类号： F02C5/02
摘要： The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit.
摘要翻译： 通过混合脉冲爆震燃烧系统的核心的流动通过压缩机，然后分离成直接通向燃烧器的主流，以及旁路流，其被路由到系统的一部分以用于 系统的酷组件。 旁路包括一个泵，其提高旁路流的压力，足以将其输送到发动机的下游站，该发动机包含比压缩机出口更高的压力的燃烧产物。
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公开(公告)号：US20120131901A1
公开(公告)日：2012-05-31
申请号：US12956868
申请日：2010-11-30
CPC分类号： F02C9/266 , F02K7/06 , F05D2260/99 , F05D2270/051
摘要： In one embodiment, a pulse detonation engine (PDE) includes a controller configured to receive signals indicative of at least one of a desired operating parameter of the PDE and a measured internal parameter of the PDE, and to adjust at least one of a first fluid flow through the PDE and a second fluid flow through at least one of multiple pulse detonation tubes disposed within the PDE based on the signals. The PDE does not include a turbine or a mechanical compressor.
摘要翻译： 在一个实施例中，脉冲爆震引擎（PDE）包括控制器，其被配置为接收指示PDE的期望操作参数和所测量的PDE的内部参数中的至少一个的信号，并且调整至少一个第一流体 基于该信号，流过PDE和通过设置在PDE内的多个脉冲爆管中的至少一个的第二流体流。 PDE不包括涡轮或机械压缩机。
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